Method and device for supplying a space propulsion engine with liquid cryogenic propellants
a technology for space propulsion engines and liquid cryogenic propellants, which is applied in the direction of machines/engines, couplings, thin material handling, etc., can solve the problems of small adjustment of thrust caused by such variations in feed pressure, and it is barely possible to obtain a thrust adjustment of around 10 to 20%, so as to reduce the distance between them or increase the
Inactive Publication Date: 2014-05-13
ASTRIUM SAS
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Benefits of technology
The present invention allows for the engine to change the thrust by adjusting the flow rate of the injected mixture without changing the pressure of the propellant injection system. This is achieved by mixing the fuel and oxidizer propellants before injection, resulting in a constant fuel-oxidizer ratio in the injected mixture. The injection system uses a plurality of needles and calibrated orifices that can adjust the flow rate of the mixture by changing the distance between the plates. Additionally, when the engine has a cooling circuit around the combustion chamber, the mixture can be fed into the cooling circuit for better control.
Problems solved by technology
Owing to the fact that, in these known engines, it is difficult to cause relatively large pressure variations in the propellant feeds without modifying the ratio of the propellants in the mixture thereof, the possible adjustment in thrust caused by such variations in feed pressure is relatively small.
In practice, it is barely possible to obtain a thrust adjustment of around 10 to 20%.
Method used
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[0026]The propellant injection means 2 comprise an enclosure 5 into which said peripheral cooling circuit 4 runs at 6. The enclosure 5 communicates with the combustion chamber 1 via a plate 7 provided with a plurality of calibrated through-orifices 8, for example distributed in concentric circles or in rows and columns (see also FIG. 3). In addition, the enclosure 5 contains a plate 9 at least approximately parallel to the plate 7 and able to be moved closer to and further away from said plate 7 (as indicated symbolically by the double-headed arrow F) thanks to an actuator 10, for example an actuating cylinder. The plate 9 has, on its face turned toward the plate 7, a plurality of needles 11 placed in correspondence with said calibrated orifices 8, so that each needle 11 can cooperate with a calibrated orifice 8 in order to define the flow area of said orifice. Of course, this flow area can be varied, under the control of the actuator 10.
[0027]In addition, FIGS. 1 and 2 show an oxid...
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Disclosed are a method and device for supplying a combustion chamber of a space propulsion engine with cryogenic liquid fuel and oxidizer propellants. The propellants are mixed at constant pressure to produce a propellant mixture, with the propellants being mixed at a location upstream of an orifice of a propellant injector. The propellant mixture is fed to an enclosure of the propellant injector, and from the propellant injector enclosure, the propellant mixture is injected into the combustion chamber. The flow rate of the propellant mixture from the propellant injector enclosure into the combustion chamber is varied by adjustment of the propellant injector, with the injection of the propellant mixture from the propellant injector enclosure into the combustion chamber being at constant pressure.
Description
FIELD OF THE INVENTION[0001]The present invention relates to space propulsion engines supplied with cryogenic liquid propellants.BACKGROUND OF THE INVENTION[0002]In known engines of this type, for example LOX-LH2 or LOX-kerosene engines currently used in launchers, the oxidizer propellant and fuel propellant are injected separately into the combustion chamber of said engines, the mixing of said propellants taking place in said combustion chamber.[0003]Owing to the fact that, in these known engines, it is difficult to cause relatively large pressure variations in the propellant feeds without modifying the ratio of the propellants in the mixture thereof, the possible adjustment in thrust caused by such variations in feed pressure is relatively small. In practice, it is barely possible to obtain a thrust adjustment of around 10 to 20%.SUMMARY OF THE INVENTION[0004]The object of the present invention is to remedy this drawback.[0005]For this purpose, according to the invention, the meth...
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IPC IPC(8): F16L37/56
CPCF05D2260/205F02K9/52Y02E60/321F02K9/50F02K9/56Y10T137/87153
Inventor LAINE, ROBERT, ANDRE
Owner ASTRIUM SAS